US5738490A - Gas turbine engine shroud seals - Google Patents

Gas turbine engine shroud seals Download PDF

Info

Publication number
US5738490A
US5738490A US08/650,441 US65044196A US5738490A US 5738490 A US5738490 A US 5738490A US 65044196 A US65044196 A US 65044196A US 5738490 A US5738490 A US 5738490A
Authority
US
United States
Prior art keywords
seal
shroud
component
annular gap
gap
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US08/650,441
Inventor
Antonio Pizzi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Assigned to PRATT & WHITNEY CANADA INC. reassignment PRATT & WHITNEY CANADA INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CRONE, JAMES, PIZZI, ANTONION
Priority to US08/650,441 priority Critical patent/US5738490A/en
Priority to US08/826,228 priority patent/US5762472A/en
Priority to PCT/CA1997/000339 priority patent/WO1997044570A1/en
Priority to JP54130897A priority patent/JP3947227B2/en
Priority to DE69706163T priority patent/DE69706163T2/en
Priority to CZ19983698A priority patent/CZ292410B6/en
Priority to PL357633A priority patent/PL192923B1/en
Priority to EP97921557A priority patent/EP0900323B1/en
Priority to CN97194791A priority patent/CN1092750C/en
Priority to PL97330007A priority patent/PL185918B1/en
Priority to CA002255077A priority patent/CA2255077C/en
Priority to RU98123201/06A priority patent/RU2169846C2/en
Priority to US08/957,771 priority patent/US5988975A/en
Publication of US5738490A publication Critical patent/US5738490A/en
Application granted granted Critical
Priority to CZ20023185A priority patent/CZ292418B6/en
Priority to JP2006247476A priority patent/JP2006342811A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to gas turbine engines, and more particularly, to turbine blade shroud seals for reducing the leakage of cooling fluid in the casing surrounding the turbine blades.
  • the engine casing surrounds the turbine section of an aircraft engine and is constructed to conduct cooling gases within the casing to various elements, such as the shrouds themselves.
  • the turbine section of the engine which is concentric to the casing, is in the path of very hot gases. It is preferred that the surrounding casing structure be maintained relatively cool.
  • the annular shroud for the turbine blade tips is normally segmented in the circumferential direction. Seals are required to prevent gas leakage at the gaps formed between the ends of the shroud segments.
  • U.S. Pat. No. 4,573,866, to Sandy, Jr. et al, issued Mar. 4, 1986 shows a feather seal in a radial plane between the ends of the blade tip shrouds.
  • U.S. Pat. No. 5,318,402 to Bailey et al, issued Jun. 7, 1994, shows a spline or feather seal and a circumferential spacer band that locks the shrouds and the feather seals together.
  • a construction in accordance with the present invention includes a seal for a turbine blade tip shroud for a gas turbine engine where the shroud is located between the axially directed hot gas path and a concentric cooling gas conduit formed between the shroud and an outer casing and wherein the shroud includes a plurality of segments arranged circumferentially with each shroud segment having an axial platform and at least one radial rib extending from the platform, the shroud segments having end walls and a groove defined in the end wall portion corresponding to the platform and continuously in the end wall portion corresponding to the rib, the seal comprising a one-piece sheet member formed to the configuration of the continuous groove in the end wall portions such that a portion of the seal has an axial component and a portion of the same seal has a radial component.
  • the vertical component of the sheet forming the seal is doubled over so that the vertical component is a resilient member providing a frictional engagement within the groove formed in the wall of the radial rib.
  • a ring seal for a gas turbine engine for sealing a joint between two annular engine parts when an annular gap is formed with an axial component, the axial gap having spaced-apart radial walls, wherein the ring seal has an axial portion including a wavy portion with one peak of the wavy portion in contact with one of the spaced-apart walls and another peak in contact with the other spaced-apart wall of the gap whereby the gap is sealed against leakage by gases flowing on either side of the joint and the wavy portion subtends an angle sufficient to allow the seal to be readily compressed radially.
  • FIG. 1 is a fragmentary perspective view, partly exploded, showing an embodiment of one aspect of the present invention
  • FIG. 2 is a front elevation of a detail shown in FIG. 1;
  • FIG. 3 is a perspective view, partly in cross-section, of an embodiment of another aspect of the present invention.
  • FIG. 4 is an axial cross-section of the turbine section of a gas turbine engine showing a detail of the present invention.
  • FIG. 5 is an enlarged fragmentary cross-sectional view taken in the same plane as FIG. 4 and showing a detail of FIG. 4.
  • FIGS. 1 and 2 there is shown a typical turbine blade shroud 12 for use in an engine 10.
  • the shroud 12 includes a plurality of segments 12a . . . 12n arranged circumferentially and concentric with the rotor on which turbine blades 38 are mounted (FIGS. 1 and 4).
  • a shroud segment as represented by the numeral 12 in FIG. 1, includes a platform 14 made up essentially of an annular flat plate-like member having an axial component and a pair of upstanding ribs 16 and 18 having flanges 20 and 22 respectively.
  • the ribs 16 and 18 and respective flanges 20 and 22 act to support the shroud platform 14 as well as to define the cooling air passages and chambers.
  • the flanges 20 and 22, as shown in FIG. 4, also serve to mount the shroud within the engine casing 32 and mounting structure 36 as will be described further.
  • the wall 34 of engine casing 32 may be provided with a vent opening 33 to allow cool air to enter the space between the support structure and the casing 32. Ventilation openings 31 are also provided in the support structure 36 to allow this cool air to enter annular channel 35 formed between the shroud 12 and support structure 36.
  • apertures 37 in the shroud 12 allow this cooling air to exhaust into the hot gas path.
  • each shroud segment 12 is provided with a continuous groove 26 which includes an axial component 26b and radial components 26a and 26c which correspond with the ribs 16 and 18 respectively.
  • the seal 24 is made up of a sheet 24 of heat resistant alloy which has been bent to provide upstanding elements 28 and 30 and horizontal members 25 and 27 which correspond with the platform 14. The seal could, of course, be extruded or molded from any suitable heat resistant material.
  • Each of the upstanding elements 28 and 30 includes legs 28a and 28b and 38a and 38b which are slightly divergent and wider than the respective groove, as shown in FIG. 2.
  • This configuration provides a degree of resilience to the upstanding elements 28 and 30 such that when the seal 24 is fitted into the groove 26 at the end of the shroud 12, the upstanding elements 28 and 30 must each be squeezed in order to be inserted into the upstanding groove segments 26a and 26c, thereby allowing a tight fit of the seal in the groove 26.
  • the segments can be easily assembled and then separated and the seal 24 replaced in the event of necessary maintenance.
  • FIGS. 3 to 5 Another aspect of the present invention is shown in FIGS. 3 to 5.
  • the turbine section of engine 10 is partly illustrated in FIG. 4 and, in addition to the turbine blades 38, stator vanes 42 and 44 are shown.
  • Each stator vane has a shroud structure mounted thereto, while the shroud 12 surrounds the blade tips 40 of turbine blades 38.
  • the mounting structure 36 within the engine casing 32 supports the shroud 12, as illustrated in FIGS. 4 and 5.
  • the flange 22 of the shroud 12 may be supported on the flange 47 of the support structure 36, for instance.
  • flange 20 may be supported the by the flange of support structure 36.
  • the ribs 16 and 18 as well as the configuration of the support structure 36 allows for cooling channels to be formed in and around the shrouds.
  • the air pressure in cooling channel 64 may be different from that around channel 66, and thus these different channels or chambers must be sealed.
  • a ring seal 46 is provided in the gap or annular recess 48 formed by the groove formed by flange 47.
  • the recess 48 when flange 22 is inserted, has an "L" shape with an axial component 48a and a radial component 48b.
  • the ring seal 46 includes a "C" shaped portion 52 which has a smaller radial dimension than the recess 48 in the area of the radial component 48b.
  • "C" shaped portion 52 includes legs 54 and 56.
  • An extension of leg 54 has a wave pattern subtending flat angles to provide wave section 58 having peaks 60 and 62.
  • the angle subtended by arms 58a and 58b is an obtuse angle. The angle may be acute, but it must be great enough that the seal is readily compressible radially.
  • wave section 58 is such that the radial extent between the peaks 60 and 62 is slightly greater than the radial dimension between walls 36a and 22a of the recess 48.
  • Ring seal 46 is made from a heat resistant material or alloy having an inherent elasticity suitable to maintain spring fitted continual contact with opposed walls 22a and 36a.
  • the wave section 58 is spring fitted into the recess 48 so that the peaks 60 and 62 are in continual contact with the opposed walls 22a and 36a.
  • Ring seal 46 may constructed as an endless ring to be fitted into recess 48.
  • the ring seal 46 may be fabricated from a sheet of resilient heat resistant alloy bent to form the herein described configuration.
  • the flange 22 may be beveled, as shown, in order to enable its insertion against the spring seal 46 already in the recess 48.
  • the radial resilience of the wave portion 58 will allow easy insertion of the flange 22 as well as easy replacement of the ring seal 46 when the shroud is removed from the recess 48 during maintenance thereof.
  • both seal 24 and ring seal 46 can cooperate with shroud 12 for easy assembly of the seals and the shroud segments allowing for greatly facilitated maintenance of the shroud 12.

Abstract

A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a platform and radially extending ribs, and the seal fits tightly in the groove providing an axial and a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross-section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Description

BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to gas turbine engines, and more particularly, to turbine blade shroud seals for reducing the leakage of cooling fluid in the casing surrounding the turbine blades.
2. Description of the Prior Art
There have been many attempts to improve the sealing capabilities of annular shrouds surrounding the tips of turbine blades. The engine casing surrounds the turbine section of an aircraft engine and is constructed to conduct cooling gases within the casing to various elements, such as the shrouds themselves. The turbine section of the engine, which is concentric to the casing, is in the path of very hot gases. It is preferred that the surrounding casing structure be maintained relatively cool.
The annular shroud for the turbine blade tips is normally segmented in the circumferential direction. Seals are required to prevent gas leakage at the gaps formed between the ends of the shroud segments. U.S. Pat. Nos. 4,767,260 to Clevenger et al, issued Aug. 30, 1988, and 5,158,430, to Dixon et al, issued Oct. 27, 1992, show variations on feather seals placed between the platforms of the vane assemblies. U.S. Pat. No. 4,573,866, to Sandy, Jr. et al, issued Mar. 4, 1986, shows a feather seal in a radial plane between the ends of the blade tip shrouds. U.S. Pat. No. 5,318,402, to Bailey et al, issued Jun. 7, 1994, shows a spline or feather seal and a circumferential spacer band that locks the shrouds and the feather seals together.
Different sealing rings are also required for different shroud and casing configurations. For instance, in a configuration involving a split joint with a groove having an axial component, it is conventional to use a "C" shaped ring. In U.S. Pat. No. 4,573,866, a bellows type ring is utilized in such a groove. Although such ring seals provide excellent sealing qualities, they tend to be stiff in compression due to the radial cross-section thereof and are, therefore, not easily replaced during engine maintenance. In fact, special tools may be required to replace such a seal.
SUMMARY OF THE INVENTION
It is an aim of the present invention to provide an improved inter-shroud segment seal of the type having an axial component and a radial component.
It is a further aim of the present invention to provide a simple one-piece sheet seal for sealing the gap formed between the ends of circumferential shroud segments in order to reduce leakage of the cooling gases into the hot gas path.
It is a further aim of the present invention to provide a ring seal for sealing annular joints formed with an annular gap having an axial component.
It is a further aim of the present invention to have a ring seal formed of sheet metal that is readily compressible in the radial direction for easier installation.
It is a further aim of the present invention to provide an improved sealing arrangement for a turbine blade tip shroud assembly.
A construction in accordance with the present invention includes a seal for a turbine blade tip shroud for a gas turbine engine where the shroud is located between the axially directed hot gas path and a concentric cooling gas conduit formed between the shroud and an outer casing and wherein the shroud includes a plurality of segments arranged circumferentially with each shroud segment having an axial platform and at least one radial rib extending from the platform, the shroud segments having end walls and a groove defined in the end wall portion corresponding to the platform and continuously in the end wall portion corresponding to the rib, the seal comprising a one-piece sheet member formed to the configuration of the continuous groove in the end wall portions such that a portion of the seal has an axial component and a portion of the same seal has a radial component.
In a more specific embodiment of the present invention, the vertical component of the sheet forming the seal is doubled over so that the vertical component is a resilient member providing a frictional engagement within the groove formed in the wall of the radial rib.
In another aspect of the present invention, a ring seal is provided for a gas turbine engine for sealing a joint between two annular engine parts when an annular gap is formed with an axial component, the axial gap having spaced-apart radial walls, wherein the ring seal has an axial portion including a wavy portion with one peak of the wavy portion in contact with one of the spaced-apart walls and another peak in contact with the other spaced-apart wall of the gap whereby the gap is sealed against leakage by gases flowing on either side of the joint and the wavy portion subtends an angle sufficient to allow the seal to be readily compressed radially.
In a more specific embodiment of the present invention, there is provided a ring seal for a turbine blade tip shroud for a gas turbine engine, where the shroud is located between the axially directed hot gas path and a concentric cooling gas conduit formed between the shroud and an outer casing and the shroud includes a platform extending axially while at least a rib extends radially so that the rib may be connected to mounting means on the casing therefrom, wherein an annular gap has an axial component formed between the shroud and the mounting means of the casing, the annular gap having opposed radially spaced walls formed on the shroud and the mounting means and whereby the ring seal has a "C" portion with a leg of the "C" portion extending axially so that the "C" portion has a greater radial dimension than that of the axial leg and the "C" portion is located in the radial component of the gap and has a radial dimension less than the radial dimension of the gap, and the leg of the ring seal includes a wave pattern with alternating peaks and the peaks being in contact with the opposed radially spaced walls of the annular gap to provide a gas seal at the joint between the shroud and the mounting means in order to prevent leakage of the cooling gas flow, and the wave pattern subtending an angle sufficient to allow the seal to be readily compressed radially.
BRIEF DESCRIPTION OF THE DRAWINGS
Having thus generally described the nature of the invention, reference will now be made to the accompanying drawings, showing by way of illustration, a preferred embodiment thereof, and in which:
FIG. 1 is a fragmentary perspective view, partly exploded, showing an embodiment of one aspect of the present invention;
FIG. 2 is a front elevation of a detail shown in FIG. 1;
FIG. 3 is a perspective view, partly in cross-section, of an embodiment of another aspect of the present invention;
FIG. 4 is an axial cross-section of the turbine section of a gas turbine engine showing a detail of the present invention; and
FIG. 5 is an enlarged fragmentary cross-sectional view taken in the same plane as FIG. 4 and showing a detail of FIG. 4.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring now to the drawings and in particular FIGS. 1 and 2, there is shown a typical turbine blade shroud 12 for use in an engine 10. The shroud 12 includes a plurality of segments 12a . . . 12n arranged circumferentially and concentric with the rotor on which turbine blades 38 are mounted (FIGS. 1 and 4).
A shroud segment, as represented by the numeral 12 in FIG. 1, includes a platform 14 made up essentially of an annular flat plate-like member having an axial component and a pair of upstanding ribs 16 and 18 having flanges 20 and 22 respectively. The ribs 16 and 18 and respective flanges 20 and 22 act to support the shroud platform 14 as well as to define the cooling air passages and chambers. The flanges 20 and 22, as shown in FIG. 4, also serve to mount the shroud within the engine casing 32 and mounting structure 36 as will be described further. The wall 34 of engine casing 32 may be provided with a vent opening 33 to allow cool air to enter the space between the support structure and the casing 32. Ventilation openings 31 are also provided in the support structure 36 to allow this cool air to enter annular channel 35 formed between the shroud 12 and support structure 36. Finally, apertures 37 in the shroud 12 allow this cooling air to exhaust into the hot gas path.
In order to provide an inter-segment seal, the end walls of each shroud segment 12 are provided with a continuous groove 26 which includes an axial component 26b and radial components 26a and 26c which correspond with the ribs 16 and 18 respectively. The seal 24 is made up of a sheet 24 of heat resistant alloy which has been bent to provide upstanding elements 28 and 30 and horizontal members 25 and 27 which correspond with the platform 14. The seal could, of course, be extruded or molded from any suitable heat resistant material.
Each of the upstanding elements 28 and 30 includes legs 28a and 28b and 38a and 38b which are slightly divergent and wider than the respective groove, as shown in FIG. 2. This configuration provides a degree of resilience to the upstanding elements 28 and 30 such that when the seal 24 is fitted into the groove 26 at the end of the shroud 12, the upstanding elements 28 and 30 must each be squeezed in order to be inserted into the upstanding groove segments 26a and 26c, thereby allowing a tight fit of the seal in the groove 26. In view of the resilience thereof, the segments can be easily assembled and then separated and the seal 24 replaced in the event of necessary maintenance.
Another aspect of the present invention is shown in FIGS. 3 to 5. The turbine section of engine 10 is partly illustrated in FIG. 4 and, in addition to the turbine blades 38, stator vanes 42 and 44 are shown. Each stator vane has a shroud structure mounted thereto, while the shroud 12 surrounds the blade tips 40 of turbine blades 38.
As shown herein, the mounting structure 36 within the engine casing 32 supports the shroud 12, as illustrated in FIGS. 4 and 5. The flange 22 of the shroud 12 may be supported on the flange 47 of the support structure 36, for instance. In the same manner, flange 20 may be supported the by the flange of support structure 36. The ribs 16 and 18 as well as the configuration of the support structure 36 allows for cooling channels to be formed in and around the shrouds. The air pressure in cooling channel 64, may be different from that around channel 66, and thus these different channels or chambers must be sealed.
A ring seal 46 is provided in the gap or annular recess 48 formed by the groove formed by flange 47. In this case, the recess 48, when flange 22 is inserted, has an "L" shape with an axial component 48a and a radial component 48b. The ring seal 46 includes a "C" shaped portion 52 which has a smaller radial dimension than the recess 48 in the area of the radial component 48b. "C" shaped portion 52 includes legs 54 and 56. An extension of leg 54 has a wave pattern subtending flat angles to provide wave section 58 having peaks 60 and 62. The angle subtended by arms 58a and 58b is an obtuse angle. The angle may be acute, but it must be great enough that the seal is readily compressible radially.
The configuration of wave section 58 is such that the radial extent between the peaks 60 and 62 is slightly greater than the radial dimension between walls 36a and 22a of the recess 48. Ring seal 46 is made from a heat resistant material or alloy having an inherent elasticity suitable to maintain spring fitted continual contact with opposed walls 22a and 36a. Thus, the wave section 58 is spring fitted into the recess 48 so that the peaks 60 and 62 are in continual contact with the opposed walls 22a and 36a.
Thus, because of the configuration of the ring seal 46, the ring seal can easily be fitted into the recess 48 before the shroud flange 22 is inserted therein during the assembly thereof. Ring seal 46 may constructed as an endless ring to be fitted into recess 48. The ring seal 46 may be fabricated from a sheet of resilient heat resistant alloy bent to form the herein described configuration.
The flange 22 may be beveled, as shown, in order to enable its insertion against the spring seal 46 already in the recess 48. The radial resilience of the wave portion 58 will allow easy insertion of the flange 22 as well as easy replacement of the ring seal 46 when the shroud is removed from the recess 48 during maintenance thereof.
Therefore, both seal 24 and ring seal 46 can cooperate with shroud 12 for easy assembly of the seals and the shroud segments allowing for greatly facilitated maintenance of the shroud 12.

Claims (4)

We claim:
1. A seal for a gas turbine engine to seal a joint between two annular engine parts, the joint between the two parts comprising an annular gap with an axial component and a radial component, each component including radially spaced-apart walls, wherein the seal includes a "C" portion having a radial extent less than the spaced-apart walls of the radial component to fit within the radial component of the annular gap, with a leg of the "C" extending axially within the axial component of the annular gap, the leg having a wavy construction with one peak of the wavy portion in contact with one of the spaced-apart walls of the axial component of the annular gap and another peak in contact with the other of the spaced-apart walls of the axial component of the annular gap, whereby the gap is sealed against leakage by gases flowing on either side of the joint.
2. The seal for a gas turbine engine as defined in claim 1, wherein the seal is an endless ring.
3. A ring seal for a turbine blade tip shroud for a gas turbine engine having a hot gas path and an outer casing, wherein the shroud is located between the hot gas path and a cooling gas conduit formed between the shroud and the outer casing, the shroud including an axially extending platform for engaging a mounting structure within the engine casing to form an annular gap having an axial and a radial component between the shroud and the mounting structure, the annular gap having opposed radially spaced walls formed on the shroud and the mounting structure, the ring seal comprising a "C" portion having a greater radial dimension than that of the axially extending platform and less than the radial dimension of the gap, the "C" portion for location in the radial component of the annular gap with the "C" portion of the ring seal having a leg extending axially within the annular component of the gap, the leg including a wavy pattern with alternating peaks for contact with the opposed radially spaced walls of the annular gap to provide a gas seal at the joint between the shroud and the mounting structure.
4. The ring seal as defined in claim 3, wherein the ring seal is made from a bent sheet of inherently elastic, heat resistant alloy.
US08/650,441 1996-05-20 1996-05-20 Gas turbine engine shroud seals Expired - Lifetime US5738490A (en)

Priority Applications (15)

Application Number Priority Date Filing Date Title
US08/650,441 US5738490A (en) 1996-05-20 1996-05-20 Gas turbine engine shroud seals
US08/826,228 US5762472A (en) 1996-05-20 1997-03-27 Gas turbine engine shroud seals
CN97194791A CN1092750C (en) 1996-05-20 1997-05-20 Gas turbine engine shroud seals
RU98123201/06A RU2169846C2 (en) 1996-05-20 1997-05-20 Sealing of gas-turbine engine case (versions)
DE69706163T DE69706163T2 (en) 1996-05-20 1997-05-20 GASKET FOR STATOR RING OF A GAS TURBINE
CZ19983698A CZ292410B6 (en) 1996-05-20 1997-05-20 Seal
PL357633A PL192923B1 (en) 1996-05-20 1997-05-20 Gas turbine engine housing assembly
EP97921557A EP0900323B1 (en) 1996-05-20 1997-05-20 Gas turbine engine shroud seals
PCT/CA1997/000339 WO1997044570A1 (en) 1996-05-20 1997-05-20 Gas turbine engine shroud seals
PL97330007A PL185918B1 (en) 1996-05-20 1997-05-20 Sealing for a gas turbine rotor shroud
CA002255077A CA2255077C (en) 1996-05-20 1997-05-20 Gas turbine engine shroud seals
JP54130897A JP3947227B2 (en) 1996-05-20 1997-05-20 Gas turbine engine shroud seal
US08/957,771 US5988975A (en) 1996-05-20 1997-10-24 Gas turbine engine shroud seals
CZ20023185A CZ292418B6 (en) 1996-05-20 2002-09-20 Seal
JP2006247476A JP2006342811A (en) 1996-05-20 2006-09-13 Seal for gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US08/650,441 US5738490A (en) 1996-05-20 1996-05-20 Gas turbine engine shroud seals

Related Child Applications (2)

Application Number Title Priority Date Filing Date
US08/826,228 Division US5762472A (en) 1996-05-20 1997-03-27 Gas turbine engine shroud seals
US08/957,771 Division US5988975A (en) 1996-05-20 1997-10-24 Gas turbine engine shroud seals

Publications (1)

Publication Number Publication Date
US5738490A true US5738490A (en) 1998-04-14

Family

ID=24608931

Family Applications (3)

Application Number Title Priority Date Filing Date
US08/650,441 Expired - Lifetime US5738490A (en) 1996-05-20 1996-05-20 Gas turbine engine shroud seals
US08/826,228 Expired - Lifetime US5762472A (en) 1996-05-20 1997-03-27 Gas turbine engine shroud seals
US08/957,771 Expired - Lifetime US5988975A (en) 1996-05-20 1997-10-24 Gas turbine engine shroud seals

Family Applications After (2)

Application Number Title Priority Date Filing Date
US08/826,228 Expired - Lifetime US5762472A (en) 1996-05-20 1997-03-27 Gas turbine engine shroud seals
US08/957,771 Expired - Lifetime US5988975A (en) 1996-05-20 1997-10-24 Gas turbine engine shroud seals

Country Status (10)

Country Link
US (3) US5738490A (en)
EP (1) EP0900323B1 (en)
JP (2) JP3947227B2 (en)
CN (1) CN1092750C (en)
CA (1) CA2255077C (en)
CZ (1) CZ292410B6 (en)
DE (1) DE69706163T2 (en)
PL (2) PL192923B1 (en)
RU (1) RU2169846C2 (en)
WO (1) WO1997044570A1 (en)

Cited By (85)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
EP0959229A3 (en) * 1998-05-19 2000-04-12 General Electric Company Low strain shroud element for a turbine
US6076835A (en) * 1997-05-21 2000-06-20 Allison Advanced Development Company Interstage van seal apparatus
EP1022437A1 (en) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Construction element for use in a thermal machine
US6203025B1 (en) * 1998-03-18 2001-03-20 Rolls-Royce Plc Seal
US6315519B1 (en) * 1998-09-28 2001-11-13 General Electric Company Turbine inner shroud and turbine assembly containing such inner shroud
DE10225679A1 (en) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Bearing ring for mounting of blade roots of variable stator blades in HP compressor of gas turbine, is divided into individual segments with box section construction and with free ends bevelled in relation to circumferential direction
EP1387044A2 (en) 2002-07-30 2004-02-04 General Electric Company Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
US20040090013A1 (en) * 2000-12-01 2004-05-13 Lawer Steven D. Seal segment for a turbine
US20060045746A1 (en) * 2004-08-24 2006-03-02 Remy Synnott Multi-point seal
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
GB2418966A (en) * 2004-10-11 2006-04-12 Rolls Royce Plc A sealing arrangement for sealing between annular components in a gas turbine engine
US20060083607A1 (en) * 2004-10-15 2006-04-20 Pratt & Whitney Canada Corp. Turbine shroud segment seal
US20060159549A1 (en) * 2005-01-14 2006-07-20 Pratt & Whitney Canada Corp. Gas turbine engine shroud sealing arrangement
WO2007101757A1 (en) * 2006-03-06 2007-09-13 Alstom Technology Ltd Gas turbine with annular heat shield and angled sealing strips
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
US20070258808A1 (en) * 2006-05-04 2007-11-08 Siemens Power Generation, Inc. Combustor spring clip seal system
US20090053042A1 (en) * 2007-08-22 2009-02-26 General Electric Company Method and apparatus for clearance control of turbine blade tip
US20100080699A1 (en) * 2008-09-30 2010-04-01 Pratt & Whitney Canada Corp. Turbine shroud gas path duct interface
US20100104426A1 (en) * 2006-07-25 2010-04-29 Siemens Power Generation, Inc. Turbine engine ring seal
US20110068540A1 (en) * 2009-09-22 2011-03-24 Colson Darryl A Staggered seal assembly
US20110206501A1 (en) * 2010-02-24 2011-08-25 Bergman Russell J Combined featherseal slot and lightening pocket
US20110233876A1 (en) * 2010-03-25 2011-09-29 Bergman Russell J Turbine sealing system
US20120107122A1 (en) * 2010-10-29 2012-05-03 General Electric Company Resilient mounting apparatus for low-ductility turbine shroud
US20120128481A1 (en) * 2008-11-26 2012-05-24 Snecma Anti-wear device for the blades of a turbine distributor in an aeronautical turbine engine
US20130209249A1 (en) * 2012-02-09 2013-08-15 Snecma Annular anti-wear shim for a turbomachine
US8562286B2 (en) 2010-04-06 2013-10-22 United Technologies Corporation Dead ended bulbed rib geometry for a gas turbine engine
US20140023480A1 (en) * 2012-07-20 2014-01-23 Michael G. McCaffrey Radial position control of case supported structure
US20140069101A1 (en) * 2012-09-13 2014-03-13 General Electric Company Compressor fairing segment
US8734089B2 (en) 2009-12-29 2014-05-27 Rolls-Royce Corporation Damper seal and vane assembly for a gas turbine engine
WO2014133958A1 (en) 2013-02-27 2014-09-04 United Technologies Corporation Assembly for sealing a gap between components of a turbine engine
US20140361119A1 (en) * 2013-06-07 2014-12-11 Pratt & Whitney Canada Corp. Mounting system for mounting engine nacelle components and associated method
US20140369810A1 (en) * 2013-06-14 2014-12-18 Rohr, Inc. Assembly for mounting a turbine engine to a pylon
US20150016970A1 (en) * 2011-12-31 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade track assembly, components, and methods
US20150132054A1 (en) * 2012-04-27 2015-05-14 General Electric Company System and method of limiting axial movement between components in a turbine assembly
US9097115B2 (en) 2011-07-01 2015-08-04 Alstom Technology Ltd Turbine vane
US9238977B2 (en) 2012-11-21 2016-01-19 General Electric Company Turbine shroud mounting and sealing arrangement
US20160047549A1 (en) * 2014-08-15 2016-02-18 Rolls-Royce Corporation Ceramic matrix composite components with inserts
US20160169037A1 (en) * 2014-12-15 2016-06-16 Pratt & Whitney Canada Corp. Turbine shroud sealing architecture
US20160222812A1 (en) * 2015-01-29 2016-08-04 Rolls-Royce Corporation Seals for gas turbine engines
US20160312640A1 (en) * 2013-12-12 2016-10-27 United Technologies Corporation Blade outer air seal with secondary air sealing
US9714580B2 (en) 2013-07-24 2017-07-25 United Technologies Corporation Trough seal for gas turbine engine
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US9752592B2 (en) 2013-01-29 2017-09-05 Rolls-Royce Corporation Turbine shroud
US20170254271A1 (en) * 2016-03-01 2017-09-07 Rolls-Royce Plc Intercomponent seal for a gas turbine engine
US20170328228A1 (en) * 2016-05-16 2017-11-16 General Electric Company Seal for hardware segments
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US20180119558A1 (en) * 2016-10-31 2018-05-03 United Technologies Corporation W-seal shield for interrupted cavity
US9988923B2 (en) 2013-08-29 2018-06-05 United Technologies Corporation Seal for gas turbine engine
US10012100B2 (en) 2015-01-15 2018-07-03 Rolls-Royce North American Technologies Inc. Turbine shroud with tubular runner-locating inserts
US20180238188A1 (en) * 2017-02-22 2018-08-23 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features
US10094233B2 (en) 2013-03-13 2018-10-09 Rolls-Royce Corporation Turbine shroud
US10138734B2 (en) 2013-03-14 2018-11-27 Safran Helicopter Engines Turbine ring for a turbomachine
US20180340437A1 (en) * 2017-02-24 2018-11-29 General Electric Company Spline for a turbine engine
US20180355755A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US20180355753A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US20180355741A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US10190434B2 (en) 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
US20190078457A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Gas turbine engine blade outer air seal
US10240476B2 (en) 2016-01-19 2019-03-26 Rolls-Royce North American Technologies Inc. Full hoop blade track with interstage cooling air
US10287906B2 (en) 2016-05-24 2019-05-14 Rolls-Royce North American Technologies Inc. Turbine shroud with full hoop ceramic matrix composite blade track and seal system
US10309244B2 (en) 2013-12-12 2019-06-04 General Electric Company CMC shroud support system
US10316682B2 (en) 2015-04-29 2019-06-11 Rolls-Royce North American Technologies Inc. Composite keystoned blade track
US10370985B2 (en) 2014-12-23 2019-08-06 Rolls-Royce Corporation Full hoop blade track with axially keyed features
US10371008B2 (en) 2014-12-23 2019-08-06 Rolls-Royce North American Technologies Inc. Turbine shroud
US10400619B2 (en) 2014-06-12 2019-09-03 General Electric Company Shroud hanger assembly
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US20190316481A1 (en) * 2018-04-17 2019-10-17 United Technologies Corporation Seal assembly for gas turbine engine
US20190316480A1 (en) * 2018-04-17 2019-10-17 United Technologies Corporation Seal assembly for gas turbine engine
US10465558B2 (en) 2014-06-12 2019-11-05 General Electric Company Multi-piece shroud hanger assembly
US10494946B2 (en) 2013-03-14 2019-12-03 General Electric Company Method of making a turbine shroud
US20200063586A1 (en) * 2018-08-24 2020-02-27 General Electric Company Spline Seal with Cooling Features for Turbine Engines
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform
US11053806B2 (en) 2015-04-29 2021-07-06 Rolls-Royce Corporation Brazed blade track for a gas turbine engine
US11092027B2 (en) * 2019-11-19 2021-08-17 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with sheet-metal sealing features
US11131215B2 (en) * 2019-11-19 2021-09-28 Rolls-Royce North American Technologies Inc. Turbine shroud cartridge assembly with sealing features
US20220025783A1 (en) * 2018-12-13 2022-01-27 Siemens Energy Global GmbH & Co. KG Seal arrangement for a split housing
US11286812B1 (en) 2021-05-25 2022-03-29 Rolls-Royce Corporation Turbine shroud assembly with axially biased pin and shroud segment
US11346251B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with radially biased ceramic matrix composite shroud segments
US11346237B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with axially biased ceramic matrix composite shroud segment
US11473437B2 (en) * 2015-09-24 2022-10-18 General Electric Company Turbine snap in spring seal
US11486258B2 (en) * 2019-09-25 2022-11-01 Man Energy Solutions Se Blade of a turbo machine
US11629607B2 (en) 2021-05-25 2023-04-18 Rolls-Royce Corporation Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments
US11668207B2 (en) 2014-06-12 2023-06-06 General Electric Company Shroud hanger assembly
US11761351B2 (en) 2021-05-25 2023-09-19 Rolls-Royce Corporation Turbine shroud assembly with radially located ceramic matrix composite shroud segments

Families Citing this family (101)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19850732A1 (en) * 1998-11-04 2000-05-11 Asea Brown Boveri Axial turbine
DE19938274A1 (en) * 1999-08-12 2001-02-15 Asea Brown Boveri Device and method for drawing the gap between the stator and rotor arrangement of a turbomachine
DE19938443A1 (en) * 1999-08-13 2001-02-15 Abb Alstom Power Ch Ag Fastening and fixing device
JP2002213207A (en) * 2001-01-15 2002-07-31 Mitsubishi Heavy Ind Ltd Gas turbine segment
GB0108398D0 (en) * 2001-04-04 2001-05-23 Siemens Ag Seal element for sealing a gap and combustion turbine having a seal element
US6508624B2 (en) 2001-05-02 2003-01-21 Siemens Automotive, Inc. Turbomachine with double-faced rotor-shroud seal structure
GB2378486A (en) * 2001-08-04 2003-02-12 Siemens Ag A seal element for sealing a gap and combustion turbine having such a seal element
US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
US6726448B2 (en) * 2002-05-15 2004-04-27 General Electric Company Ceramic turbine shroud
US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
US6883807B2 (en) 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US6821085B2 (en) * 2002-09-30 2004-11-23 General Electric Company Turbine engine axially sealing assembly including an axially floating shroud, and assembly method
DE10303340A1 (en) * 2003-01-29 2004-08-26 Alstom Technology Ltd cooling device
US20050091984A1 (en) * 2003-11-03 2005-05-05 Robert Czachor Heat shield for gas turbine engine
DE102004010236A1 (en) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt
US7374395B2 (en) * 2005-07-19 2008-05-20 Pratt & Whitney Canada Corp. Turbine shroud segment feather seal located in radial shroud legs
US7338253B2 (en) * 2005-09-15 2008-03-04 General Electric Company Resilient seal on trailing edge of turbine inner shroud and method for shroud post impingement cavity sealing
US7278820B2 (en) * 2005-10-04 2007-10-09 Siemens Power Generation, Inc. Ring seal system with reduced cooling requirements
US7534086B2 (en) * 2006-05-05 2009-05-19 Siemens Energy, Inc. Multi-layer ring seal
US7665955B2 (en) * 2006-08-17 2010-02-23 Siemens Energy, Inc. Vortex cooled turbine blade outer air seal for a turbine engine
US7922444B2 (en) 2007-01-19 2011-04-12 United Technologies Corporation Chamfer rail pockets for turbine vane shrouds
FR2913717A1 (en) * 2007-03-15 2008-09-19 Snecma Propulsion Solide Sa Ring assembly for e.g. aircraft engine gas turbine, has centering unit constituted of metallic ring gear and bracket, and centering complete ring, where elastically deformable tab blocks rotation of ring around axis of ring
US7758307B2 (en) * 2007-05-17 2010-07-20 Siemens Energy, Inc. Wear minimization system for a compressor diaphragm
US20090053045A1 (en) * 2007-08-22 2009-02-26 General Electric Company Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud
US8128343B2 (en) * 2007-09-21 2012-03-06 Siemens Energy, Inc. Ring segment coolant seal configuration
US8308428B2 (en) 2007-10-09 2012-11-13 United Technologies Corporation Seal assembly retention feature and assembly method
US8206087B2 (en) 2008-04-11 2012-06-26 Siemens Energy, Inc. Sealing arrangement for turbine engine having ceramic components
US8240985B2 (en) * 2008-04-29 2012-08-14 Pratt & Whitney Canada Corp. Shroud segment arrangement for gas turbine engines
US8162598B2 (en) * 2008-09-25 2012-04-24 Siemens Energy, Inc. Gas turbine sealing apparatus
FR2938873B1 (en) * 2008-11-21 2014-06-27 Turbomeca POSITIONING DEVICE FOR RING SEGMENT
EP2218882A1 (en) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Stator vane carrier system
JP5384983B2 (en) * 2009-03-27 2014-01-08 本田技研工業株式会社 Turbine shroud
US20110044803A1 (en) * 2009-08-18 2011-02-24 Pratt & Whitney Canada Corp. Blade outer air seal anti-rotation
US8684680B2 (en) * 2009-08-27 2014-04-01 Pratt & Whitney Canada Corp. Sealing and cooling at the joint between shroud segments
FR2949810B1 (en) * 2009-09-04 2013-06-28 Turbomeca DEVICE FOR SUPPORTING A TURBINE RING, TURBINE WITH SUCH A DEVICE AND TURBOMOTOR WITH SUCH A TURBINE
US8500392B2 (en) * 2009-10-01 2013-08-06 Pratt & Whitney Canada Corp. Sealing for vane segments
US8434999B2 (en) * 2010-03-25 2013-05-07 General Electric Company Bimetallic spline seal
FR2957969B1 (en) * 2010-03-26 2013-03-29 Snecma DEVICE FOR SEALING BETWEEN ADJACENT BLADE HEADS IN MATERIAL COMPOSED OF A TURBOMACHINE MOBILE WHEEL
FR2961556B1 (en) * 2010-06-16 2015-12-11 Snecma ISOLATION OF THE EXTERNAL HOUSING OF A TURBOMACHINE TURBINE WITH A SECTORIZED RING
DE102010031124A1 (en) * 2010-07-08 2012-01-12 Man Diesel & Turbo Se flow machine
US9079245B2 (en) 2011-08-31 2015-07-14 Pratt & Whitney Canada Corp. Turbine shroud segment with inter-segment overlap
GB201117084D0 (en) 2011-10-05 2011-11-16 Rolls Royce Plc Strip seals
US8899914B2 (en) * 2012-01-05 2014-12-02 United Technologies Corporation Stator vane integrated attachment liner and spring damper
US8967951B2 (en) * 2012-01-10 2015-03-03 General Electric Company Turbine assembly and method for supporting turbine components
US8979486B2 (en) 2012-01-10 2015-03-17 United Technologies Corporation Intersegment spring “T” seal
US9051849B2 (en) * 2012-02-13 2015-06-09 United Technologies Corporation Anti-rotation stator segments
RU2506434C2 (en) * 2012-04-04 2014-02-10 Николай Борисович Болотин Gas turbine engine
RU2498085C1 (en) * 2012-04-04 2013-11-10 Николай Борисович Болотин Gas-turbine engine
RU2506433C2 (en) * 2012-04-04 2014-02-10 Николай Борисович Болотин Gas turbine engine
RU2499891C1 (en) * 2012-04-12 2013-11-27 Николай Борисович Болотин Gas turbine engine turbine
US9127549B2 (en) * 2012-04-26 2015-09-08 General Electric Company Turbine shroud cooling assembly for a gas turbine system
EP2685052A1 (en) * 2012-07-10 2014-01-15 Siemens Aktiengesellschaft A heat shield and a method for construction thereof
US9464536B2 (en) 2012-10-18 2016-10-11 General Electric Company Sealing arrangement for a turbine system and method of sealing between two turbine components
US9587504B2 (en) * 2012-11-13 2017-03-07 United Technologies Corporation Carrier interlock
US9863264B2 (en) * 2012-12-10 2018-01-09 General Electric Company Turbine shroud engagement arrangement and method
US9500095B2 (en) 2013-03-13 2016-11-22 Pratt & Whitney Canada Corp. Turbine shroud segment sealing
US20160040547A1 (en) * 2013-04-12 2016-02-11 United Technologies Corporation Blade outer air seal with secondary air sealing
EP2997234B1 (en) 2013-05-17 2020-05-27 General Electric Company Cmc shroud support system of a gas turbine
US8814507B1 (en) * 2013-05-28 2014-08-26 Siemens Energy, Inc. Cooling system for three hook ring segment
EP3030754B1 (en) * 2013-08-06 2018-11-14 United Technologies Corporation Boas with radial load feature
US9938846B2 (en) 2014-06-27 2018-04-10 Rolls-Royce North American Technologies Inc. Turbine shroud with sealed blade track
CN104454033B (en) * 2014-11-03 2017-02-15 中国南方航空工业(集团)有限公司 Sealing ring and gas turbine with same
US10196913B1 (en) * 2014-12-17 2019-02-05 United Technologies Corporation Featherseal having tapered radial portion
US10281045B2 (en) 2015-02-20 2019-05-07 Rolls-Royce North American Technologies Inc. Apparatus and methods for sealing components in gas turbine engines
US9863265B2 (en) 2015-04-15 2018-01-09 General Electric Company Shroud assembly and shroud for gas turbine engine
US9828879B2 (en) * 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips
US9932901B2 (en) 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
FR3036436B1 (en) * 2015-05-22 2020-01-24 Safran Ceramics TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES
US10370994B2 (en) * 2015-05-28 2019-08-06 Rolls-Royce North American Technologies Inc. Pressure activated seals for a gas turbine engine
US9759079B2 (en) 2015-05-28 2017-09-12 Rolls-Royce Corporation Split line flow path seals
US10215056B2 (en) 2015-06-30 2019-02-26 Rolls-Royce Corporation Turbine shroud with movable attachment features
GB201514093D0 (en) 2015-08-10 2015-09-23 Rolls Royce Plc A Sealing Attachment for a Gas Turbine Engine
US10443417B2 (en) * 2015-09-18 2019-10-15 General Electric Company Ceramic matrix composite ring shroud retention methods-finger seals with stepped shroud interface
US20170089211A1 (en) * 2015-09-24 2017-03-30 General Electric Company Turbine snap in spring seal
US10458263B2 (en) 2015-10-12 2019-10-29 Rolls-Royce North American Technologies Inc. Turbine shroud with sealing features
US10689994B2 (en) 2016-03-31 2020-06-23 General Electric Company Seal assembly to seal corner leaks in gas turbine
FR3055148B1 (en) * 2016-08-19 2020-06-05 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3055147B1 (en) * 2016-08-19 2020-05-29 Safran Aircraft Engines TURBINE RING ASSEMBLY
US10301955B2 (en) 2016-11-29 2019-05-28 Rolls-Royce North American Technologies Inc. Seal assembly for gas turbine engine components
US10443420B2 (en) * 2017-01-11 2019-10-15 Rolls-Royce North American Technologies Inc. Seal assembly for gas turbine engine components
US11015613B2 (en) 2017-01-12 2021-05-25 General Electric Company Aero loading shroud sealing
US10577977B2 (en) 2017-02-22 2020-03-03 Rolls-Royce Corporation Turbine shroud with biased retaining ring
US11225880B1 (en) 2017-02-22 2022-01-18 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine having a tip clearance probe
US10533446B2 (en) 2017-05-15 2020-01-14 United Technologies Corporation Alternative W-seal groove arrangement
US10900378B2 (en) 2017-06-16 2021-01-26 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having internal cooling passages
US10677084B2 (en) 2017-06-16 2020-06-09 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement
US10655489B2 (en) 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US10633994B2 (en) 2018-03-21 2020-04-28 United Technologies Corporation Feather seal assembly
RU184419U9 (en) * 2018-05-18 2018-11-14 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Gas turbine engine rotor insert
US11111806B2 (en) * 2018-08-06 2021-09-07 Raytheon Technologies Corporation Blade outer air seal with circumferential hook assembly
US11105209B2 (en) 2018-08-28 2021-08-31 General Electric Company Turbine blade tip shroud
US10920600B2 (en) * 2018-09-05 2021-02-16 Raytheon Technologies Corporation Integrated seal and wear liner
US10794206B2 (en) 2018-09-05 2020-10-06 Raytheon Technologies Corporation CMC BOAS intersegment seal
GB201820224D0 (en) * 2018-12-12 2019-01-23 Rolls Royce Plc Seal segment for shroud ring of a gas turbine engine
US11840930B2 (en) * 2019-05-17 2023-12-12 Rtx Corporation Component with feather seal slots for a gas turbine engine
GB201907545D0 (en) * 2019-05-29 2019-07-10 Siemens Ag Heatshield for a gas turbine engine
US11326463B2 (en) * 2019-06-19 2022-05-10 Raytheon Technologies Corporation BOAS thermal baffle
CN110847982B (en) * 2019-11-04 2022-04-19 中国科学院工程热物理研究所 Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor
JP2021195920A (en) * 2020-06-16 2021-12-27 東芝エネルギーシステムズ株式会社 Turbine stationary blade
US11156110B1 (en) 2020-08-04 2021-10-26 General Electric Company Rotor assembly for a turbine section of a gas turbine engine
US11655719B2 (en) 2021-04-16 2023-05-23 General Electric Company Airfoil assembly

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3712757A (en) * 1969-10-28 1973-01-23 Secr Defence Bladed rotors for fluid flow machines
US3754766A (en) * 1971-11-11 1973-08-28 United Aircraft Corp Spring type ring seal
US3869222A (en) * 1973-06-07 1975-03-04 Ford Motor Co Seal means for a gas turbine engine
US4311432A (en) * 1979-11-20 1982-01-19 United Technologies Corporation Radial seal
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
US4551064A (en) * 1982-03-05 1985-11-05 Rolls-Royce Limited Turbine shroud and turbine shroud assembly
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US5145316A (en) * 1989-12-08 1992-09-08 Rolls-Royce Plc Gas turbine engine blade shroud assembly
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5176495A (en) * 1991-07-09 1993-01-05 General Electric Company Thermal shielding apparatus or radiositor for a gas turbine engine
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5192185A (en) * 1990-11-01 1993-03-09 Rolls-Royce Plc Shroud liners
US5197853A (en) * 1991-08-28 1993-03-30 General Electric Company Airtight shroud support rail and method for assembling in turbine engine
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
US5273396A (en) * 1992-06-22 1993-12-28 General Electric Company Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US5318402A (en) * 1992-09-21 1994-06-07 General Electric Company Compressor liner spacing device
US5738490A (en) * 1996-05-20 1998-04-14 Pratt & Whitney Canada, Inc. Gas turbine engine shroud seals

Patent Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3712757A (en) * 1969-10-28 1973-01-23 Secr Defence Bladed rotors for fluid flow machines
US3754766A (en) * 1971-11-11 1973-08-28 United Aircraft Corp Spring type ring seal
US3869222A (en) * 1973-06-07 1975-03-04 Ford Motor Co Seal means for a gas turbine engine
US4311432A (en) * 1979-11-20 1982-01-19 United Technologies Corporation Radial seal
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4551064A (en) * 1982-03-05 1985-11-05 Rolls-Royce Limited Turbine shroud and turbine shroud assembly
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US5145316A (en) * 1989-12-08 1992-09-08 Rolls-Royce Plc Gas turbine engine blade shroud assembly
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5192185A (en) * 1990-11-01 1993-03-09 Rolls-Royce Plc Shroud liners
US5176495A (en) * 1991-07-09 1993-01-05 General Electric Company Thermal shielding apparatus or radiositor for a gas turbine engine
US5197853A (en) * 1991-08-28 1993-03-30 General Electric Company Airtight shroud support rail and method for assembling in turbine engine
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
US5273396A (en) * 1992-06-22 1993-12-28 General Electric Company Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal

Cited By (136)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
US6076835A (en) * 1997-05-21 2000-06-20 Allison Advanced Development Company Interstage van seal apparatus
US6203025B1 (en) * 1998-03-18 2001-03-20 Rolls-Royce Plc Seal
EP0959229A3 (en) * 1998-05-19 2000-04-12 General Electric Company Low strain shroud element for a turbine
US6315519B1 (en) * 1998-09-28 2001-11-13 General Electric Company Turbine inner shroud and turbine assembly containing such inner shroud
EP1022437A1 (en) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Construction element for use in a thermal machine
US20040090013A1 (en) * 2000-12-01 2004-05-13 Lawer Steven D. Seal segment for a turbine
US6742783B1 (en) * 2000-12-01 2004-06-01 Rolls-Royce Plc Seal segment for a turbine
DE10225679A1 (en) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Bearing ring for mounting of blade roots of variable stator blades in HP compressor of gas turbine, is divided into individual segments with box section construction and with free ends bevelled in relation to circumferential direction
CN100554648C (en) * 2002-07-30 2009-10-28 通用电气公司 The end clearance sealing and the improvement thereof of the static sealing bar section on turbine bucket top
EP1387044A2 (en) 2002-07-30 2004-02-04 General Electric Company Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
EP1387044A3 (en) * 2002-07-30 2005-10-26 General Electric Company Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
US7238003B2 (en) * 2004-08-24 2007-07-03 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20060045746A1 (en) * 2004-08-24 2006-03-02 Remy Synnott Multi-point seal
US7172388B2 (en) * 2004-08-24 2007-02-06 Pratt & Whitney Canada Corp. Multi-point seal
US7347662B2 (en) 2004-10-11 2008-03-25 Rolls-Royce Plc Sealing arrangement
GB2418966B (en) * 2004-10-11 2006-11-15 Rolls Royce Plc A sealing arrangement
US20060078421A1 (en) * 2004-10-11 2006-04-13 Rolls-Royce Plc Sealing arrangement
GB2418966A (en) * 2004-10-11 2006-04-12 Rolls Royce Plc A sealing arrangement for sealing between annular components in a gas turbine engine
US7207771B2 (en) 2004-10-15 2007-04-24 Pratt & Whitney Canada Corp. Turbine shroud segment seal
US20060083607A1 (en) * 2004-10-15 2006-04-20 Pratt & Whitney Canada Corp. Turbine shroud segment seal
US20060159549A1 (en) * 2005-01-14 2006-07-20 Pratt & Whitney Canada Corp. Gas turbine engine shroud sealing arrangement
US7217089B2 (en) 2005-01-14 2007-05-15 Pratt & Whitney Canada Corp. Gas turbine engine shroud sealing arrangement
WO2007101757A1 (en) * 2006-03-06 2007-09-13 Alstom Technology Ltd Gas turbine with annular heat shield and angled sealing strips
US20090033036A1 (en) * 2006-03-06 2009-02-05 Peter Marx Gas turbine with annular heat shield
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
US7604456B2 (en) 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
US20070258808A1 (en) * 2006-05-04 2007-11-08 Siemens Power Generation, Inc. Combustor spring clip seal system
US7524167B2 (en) 2006-05-04 2009-04-28 Siemens Energy, Inc. Combustor spring clip seal system
US20090175721A1 (en) * 2006-05-04 2009-07-09 Rajeev Ohri Combustor spring clip seal system
US20100104426A1 (en) * 2006-07-25 2010-04-29 Siemens Power Generation, Inc. Turbine engine ring seal
US7726936B2 (en) 2006-07-25 2010-06-01 Siemens Energy, Inc. Turbine engine ring seal
US20090053042A1 (en) * 2007-08-22 2009-02-26 General Electric Company Method and apparatus for clearance control of turbine blade tip
US20100080699A1 (en) * 2008-09-30 2010-04-01 Pratt & Whitney Canada Corp. Turbine shroud gas path duct interface
US8157511B2 (en) 2008-09-30 2012-04-17 Pratt & Whitney Canada Corp. Turbine shroud gas path duct interface
US20120128481A1 (en) * 2008-11-26 2012-05-24 Snecma Anti-wear device for the blades of a turbine distributor in an aeronautical turbine engine
US9062553B2 (en) * 2008-11-26 2015-06-23 Snecma Anti-wear device for the blades of a turbine distributor in an aeronautical turbine engine
US20110068540A1 (en) * 2009-09-22 2011-03-24 Colson Darryl A Staggered seal assembly
US8083236B2 (en) 2009-09-22 2011-12-27 Hamilton Sundstrand Corporation Staggered seal assembly
US8734089B2 (en) 2009-12-29 2014-05-27 Rolls-Royce Corporation Damper seal and vane assembly for a gas turbine engine
US20110206501A1 (en) * 2010-02-24 2011-08-25 Bergman Russell J Combined featherseal slot and lightening pocket
US10030529B2 (en) 2010-02-24 2018-07-24 United Technologies Corporation Combined featherseal slot and lightening pocket
US9441497B2 (en) 2010-02-24 2016-09-13 United Technologies Corporation Combined featherseal slot and lightening pocket
US20110233876A1 (en) * 2010-03-25 2011-09-29 Bergman Russell J Turbine sealing system
US8794640B2 (en) 2010-03-25 2014-08-05 United Technologies Corporation Turbine sealing system
US8562286B2 (en) 2010-04-06 2013-10-22 United Technologies Corporation Dead ended bulbed rib geometry for a gas turbine engine
US20120107122A1 (en) * 2010-10-29 2012-05-03 General Electric Company Resilient mounting apparatus for low-ductility turbine shroud
US8998573B2 (en) * 2010-10-29 2015-04-07 General Electric Company Resilient mounting apparatus for low-ductility turbine shroud
US9097115B2 (en) 2011-07-01 2015-08-04 Alstom Technology Ltd Turbine vane
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US20180010474A1 (en) * 2011-12-31 2018-01-11 Rolls-Royce North American Technologies Inc. Blade track assembly, components, and methods
US20150016970A1 (en) * 2011-12-31 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade track assembly, components, and methods
US10837302B2 (en) 2011-12-31 2020-11-17 Rolls-Royce North American Technologies Inc. Blade track assembly, components, and methods
EP2800903B1 (en) * 2011-12-31 2018-12-05 Rolls-Royce Corporation Blade track apparatus and method of assembling a blade track apparatus
US9784115B2 (en) * 2011-12-31 2017-10-10 Rolls-Royce North American Technologies Inc. Blade track assembly, components, and methods
US20130209249A1 (en) * 2012-02-09 2013-08-15 Snecma Annular anti-wear shim for a turbomachine
US9212564B2 (en) * 2012-02-09 2015-12-15 Snecma Annular anti-wear shim for a turbomachine
US10344621B2 (en) * 2012-04-27 2019-07-09 General Electric Company System and method of limiting axial movement between components in a turbine assembly
US20150132054A1 (en) * 2012-04-27 2015-05-14 General Electric Company System and method of limiting axial movement between components in a turbine assembly
US20140023480A1 (en) * 2012-07-20 2014-01-23 Michael G. McCaffrey Radial position control of case supported structure
US9200530B2 (en) * 2012-07-20 2015-12-01 United Technologies Corporation Radial position control of case supported structure
US9528376B2 (en) * 2012-09-13 2016-12-27 General Electric Company Compressor fairing segment
US20140069101A1 (en) * 2012-09-13 2014-03-13 General Electric Company Compressor fairing segment
US9238977B2 (en) 2012-11-21 2016-01-19 General Electric Company Turbine shroud mounting and sealing arrangement
US9752592B2 (en) 2013-01-29 2017-09-05 Rolls-Royce Corporation Turbine shroud
US10280778B2 (en) 2013-02-27 2019-05-07 United Technologies Corporation Assembly for sealing a gap between components of a turbine engine
WO2014133958A1 (en) 2013-02-27 2014-09-04 United Technologies Corporation Assembly for sealing a gap between components of a turbine engine
US10094233B2 (en) 2013-03-13 2018-10-09 Rolls-Royce Corporation Turbine shroud
US10494946B2 (en) 2013-03-14 2019-12-03 General Electric Company Method of making a turbine shroud
US10138734B2 (en) 2013-03-14 2018-11-27 Safran Helicopter Engines Turbine ring for a turbomachine
US20140361119A1 (en) * 2013-06-07 2014-12-11 Pratt & Whitney Canada Corp. Mounting system for mounting engine nacelle components and associated method
US8979020B2 (en) * 2013-06-07 2015-03-17 Pratt & Whitney Canada Corp. Mounting system for mounting engine nacelle components and associated method
US20140369810A1 (en) * 2013-06-14 2014-12-18 Rohr, Inc. Assembly for mounting a turbine engine to a pylon
US10144524B2 (en) * 2013-06-14 2018-12-04 Rohr, Inc. Assembly for mounting a turbine engine to a pylon
US9714580B2 (en) 2013-07-24 2017-07-25 United Technologies Corporation Trough seal for gas turbine engine
US9988923B2 (en) 2013-08-29 2018-06-05 United Technologies Corporation Seal for gas turbine engine
US10253645B2 (en) * 2013-12-12 2019-04-09 United Technologies Corporation Blade outer air seal with secondary air sealing
US20160312640A1 (en) * 2013-12-12 2016-10-27 United Technologies Corporation Blade outer air seal with secondary air sealing
US10309244B2 (en) 2013-12-12 2019-06-04 General Electric Company CMC shroud support system
US11668207B2 (en) 2014-06-12 2023-06-06 General Electric Company Shroud hanger assembly
US11092029B2 (en) 2014-06-12 2021-08-17 General Electric Company Shroud hanger assembly
US10400619B2 (en) 2014-06-12 2019-09-03 General Electric Company Shroud hanger assembly
US10465558B2 (en) 2014-06-12 2019-11-05 General Electric Company Multi-piece shroud hanger assembly
US20160047549A1 (en) * 2014-08-15 2016-02-18 Rolls-Royce Corporation Ceramic matrix composite components with inserts
US10190434B2 (en) 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
US9845696B2 (en) * 2014-12-15 2017-12-19 Pratt & Whitney Canada Corp. Turbine shroud sealing architecture
US20160169037A1 (en) * 2014-12-15 2016-06-16 Pratt & Whitney Canada Corp. Turbine shroud sealing architecture
US10533444B2 (en) 2014-12-15 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud sealing architecture
US10370985B2 (en) 2014-12-23 2019-08-06 Rolls-Royce Corporation Full hoop blade track with axially keyed features
US10371008B2 (en) 2014-12-23 2019-08-06 Rolls-Royce North American Technologies Inc. Turbine shroud
US10012100B2 (en) 2015-01-15 2018-07-03 Rolls-Royce North American Technologies Inc. Turbine shroud with tubular runner-locating inserts
US10738642B2 (en) 2015-01-15 2020-08-11 Rolls-Royce Corporation Turbine engine assembly with tubular locating inserts
US20160222812A1 (en) * 2015-01-29 2016-08-04 Rolls-Royce Corporation Seals for gas turbine engines
US10100660B2 (en) * 2015-01-29 2018-10-16 Rolls-Royce Corporation Seals for gas turbine engines
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US11053806B2 (en) 2015-04-29 2021-07-06 Rolls-Royce Corporation Brazed blade track for a gas turbine engine
US10316682B2 (en) 2015-04-29 2019-06-11 Rolls-Royce North American Technologies Inc. Composite keystoned blade track
US11473437B2 (en) * 2015-09-24 2022-10-18 General Electric Company Turbine snap in spring seal
US10240476B2 (en) 2016-01-19 2019-03-26 Rolls-Royce North American Technologies Inc. Full hoop blade track with interstage cooling air
US20170254271A1 (en) * 2016-03-01 2017-09-07 Rolls-Royce Plc Intercomponent seal for a gas turbine engine
US10844738B2 (en) * 2016-03-01 2020-11-24 Rolls-Royce Plc Intercomponent seal for a gas turbine engine
US10221712B2 (en) * 2016-05-16 2019-03-05 General Electric Company Seal for hardware segments
US20170328228A1 (en) * 2016-05-16 2017-11-16 General Electric Company Seal for hardware segments
US10287906B2 (en) 2016-05-24 2019-05-14 Rolls-Royce North American Technologies Inc. Turbine shroud with full hoop ceramic matrix composite blade track and seal system
US10995627B2 (en) 2016-07-22 2021-05-04 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US10450883B2 (en) * 2016-10-31 2019-10-22 United Technologies Corporation W-seal shield for interrupted cavity
US20180119558A1 (en) * 2016-10-31 2018-05-03 United Technologies Corporation W-seal shield for interrupted cavity
US20180238188A1 (en) * 2017-02-22 2018-08-23 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features
US10655491B2 (en) * 2017-02-22 2020-05-19 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features
US20180340437A1 (en) * 2017-02-24 2018-11-29 General Electric Company Spline for a turbine engine
US10648362B2 (en) * 2017-02-24 2020-05-12 General Electric Company Spline for a turbine engine
US10655495B2 (en) * 2017-02-24 2020-05-19 General Electric Company Spline for a turbine engine
US20180355741A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US20180355753A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US20180355755A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
US10753222B2 (en) * 2017-09-11 2020-08-25 Raytheon Technologies Corporation Gas turbine engine blade outer air seal
US20190078457A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Gas turbine engine blade outer air seal
US10689997B2 (en) * 2018-04-17 2020-06-23 Raytheon Technologies Corporation Seal assembly for gas turbine engine
US20190316481A1 (en) * 2018-04-17 2019-10-17 United Technologies Corporation Seal assembly for gas turbine engine
US10801351B2 (en) * 2018-04-17 2020-10-13 Raytheon Technologies Corporation Seal assembly for gas turbine engine
US20190316480A1 (en) * 2018-04-17 2019-10-17 United Technologies Corporation Seal assembly for gas turbine engine
US10982559B2 (en) * 2018-08-24 2021-04-20 General Electric Company Spline seal with cooling features for turbine engines
US20200063586A1 (en) * 2018-08-24 2020-02-27 General Electric Company Spline Seal with Cooling Features for Turbine Engines
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform
US20220025783A1 (en) * 2018-12-13 2022-01-27 Siemens Energy Global GmbH & Co. KG Seal arrangement for a split housing
US11859504B2 (en) * 2018-12-13 2024-01-02 Siemens Energy Global GmbH & Co. KG Seal arrangement for a split housing
US11486258B2 (en) * 2019-09-25 2022-11-01 Man Energy Solutions Se Blade of a turbo machine
US11131215B2 (en) * 2019-11-19 2021-09-28 Rolls-Royce North American Technologies Inc. Turbine shroud cartridge assembly with sealing features
US11092027B2 (en) * 2019-11-19 2021-08-17 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with sheet-metal sealing features
US11286812B1 (en) 2021-05-25 2022-03-29 Rolls-Royce Corporation Turbine shroud assembly with axially biased pin and shroud segment
US11346251B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with radially biased ceramic matrix composite shroud segments
US11346237B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with axially biased ceramic matrix composite shroud segment
US11629607B2 (en) 2021-05-25 2023-04-18 Rolls-Royce Corporation Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments
US11761351B2 (en) 2021-05-25 2023-09-19 Rolls-Royce Corporation Turbine shroud assembly with radially located ceramic matrix composite shroud segments

Also Published As

Publication number Publication date
US5762472A (en) 1998-06-09
JP2000511256A (en) 2000-08-29
DE69706163T2 (en) 2002-05-02
EP0900323B1 (en) 2001-08-16
PL192923B1 (en) 2006-12-29
DE69706163D1 (en) 2001-09-20
CN1092750C (en) 2002-10-16
RU2169846C2 (en) 2001-06-27
JP3947227B2 (en) 2007-07-18
WO1997044570A1 (en) 1997-11-27
CA2255077C (en) 2007-09-25
CZ369898A3 (en) 1999-04-14
US5988975A (en) 1999-11-23
EP0900323A1 (en) 1999-03-10
JP2006342811A (en) 2006-12-21
CZ292410B6 (en) 2003-09-17
CN1219215A (en) 1999-06-09
PL185918B1 (en) 2003-08-29
PL330007A1 (en) 1999-04-26
CA2255077A1 (en) 1997-11-27

Similar Documents

Publication Publication Date Title
US5738490A (en) Gas turbine engine shroud seals
US4875830A (en) Flanged ladder seal
EP1327748B1 (en) Seal for gas turbine nozzle and shroud interface
EP1323894B1 (en) Supplemental seal for the chordal hinge seals in a gas turbine
US4218189A (en) Sealing means for bladed rotor for a gas turbine engine
RU98123201A (en) GAS-TURBINE ENGINE SHAFT SEAL (OPTIONS)
RU2326245C2 (en) Seal between rotating component and fixed component and steam gland in turbine, applying this seal
EP0640172A1 (en) Rotors for gas turbine engines.
US6719295B2 (en) Supplemental seal for the chordal hinge seals in a gas turbine
KR101120083B1 (en) Provision of sealing for the cabin-air bleed cavity using a segment seal
US6637753B2 (en) Supplemental seal for the chordal hinge seals in a gas turbine
JP4293419B2 (en) Auxiliary seal for string hinge seal in gas turbine
US20080112800A1 (en) Finned Seals for Turbomachinery
KR20050028785A (en) Provision of sealing for the cabin-air bleed cavity of a jet engine using a brush seal
EP1323897B1 (en) Turbine with a supplemental seal for the chordal hinge sealing
US20180274380A1 (en) Seal on the inner ring of a guide vane
KR100473751B1 (en) Gas turbine engine shroud seals
CZ292418B6 (en) Seal

Legal Events

Date Code Title Description
AS Assignment

Owner name: PRATT & WHITNEY CANADA INC., CANADA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:PIZZI, ANTONION;CRONE, JAMES;REEL/FRAME:008122/0760

Effective date: 19960515

STCF Information on status: patent grant

Free format text: PATENTED CASE

FPAY Fee payment

Year of fee payment: 4

FPAY Fee payment

Year of fee payment: 8

FPAY Fee payment

Year of fee payment: 12